EP3995671A1 - System und verfahren zur steifigkeitssteuerung - Google Patents

System und verfahren zur steifigkeitssteuerung Download PDF

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Publication number
EP3995671A1
EP3995671A1 EP20205717.0A EP20205717A EP3995671A1 EP 3995671 A1 EP3995671 A1 EP 3995671A1 EP 20205717 A EP20205717 A EP 20205717A EP 3995671 A1 EP3995671 A1 EP 3995671A1
Authority
EP
European Patent Office
Prior art keywords
component
displacement
stiffness
active device
respect
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
EP20205717.0A
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English (en)
French (fr)
Inventor
Lucia Ciciriello
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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Filing date
Publication date
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Priority to EP20205717.0A priority Critical patent/EP3995671A1/de
Publication of EP3995671A1 publication Critical patent/EP3995671A1/de
Pending legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • F01D25/164—Flexible supports; Vibration damping means associated with the bearing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/08—Restoring position
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/06—Arrangements of bearings; Lubricating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C19/00—Bearings with rolling contact, for exclusively rotary movement
    • F16C19/52—Bearings with rolling contact, for exclusively rotary movement with devices affected by abnormal or undesired conditions
    • F16C19/522—Bearings with rolling contact, for exclusively rotary movement with devices affected by abnormal or undesired conditions related to load on the bearing, e.g. bearings with load sensors or means to protect the bearing against overload
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C19/00—Bearings with rolling contact, for exclusively rotary movement
    • F16C19/52—Bearings with rolling contact, for exclusively rotary movement with devices affected by abnormal or undesired conditions
    • F16C19/525—Bearings with rolling contact, for exclusively rotary movement with devices affected by abnormal or undesired conditions related to temperature and heat, e.g. insulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C19/00—Bearings with rolling contact, for exclusively rotary movement
    • F16C19/52—Bearings with rolling contact, for exclusively rotary movement with devices affected by abnormal or undesired conditions
    • F16C19/527—Bearings with rolling contact, for exclusively rotary movement with devices affected by abnormal or undesired conditions related to vibration and noise
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C25/00—Bearings for exclusively rotary movement adjustable for wear or play
    • F16C25/06—Ball or roller bearings
    • F16C25/08—Ball or roller bearings self-adjusting
    • F16C25/086—Ball or roller bearings self-adjusting with magnetic means to preload the bearing
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K11/00—Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection
    • H02K11/20—Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection for measuring, monitoring, testing, protecting or switching
    • H02K11/25—Devices for sensing temperature, or actuated thereby
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
    • H02K7/08—Structural association with bearings
    • H02K7/09—Structural association with bearings with magnetic bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/50—Bearings
    • F05D2240/51—Magnetic
    • F05D2240/515—Electromagnetic
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/50—Bearings
    • F05D2240/54—Radial bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/303—Temperature
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/305—Tolerances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/334—Vibration measurements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/60—Control system actuates means
    • F05D2270/62—Electrical actuators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/70—Type of control algorithm
    • F05D2270/708—Type of control algorithm with comparison tables
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2360/00—Engines or pumps
    • F16C2360/23—Gas turbine engines
    • F16C2360/24—Turbochargers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2361/00—Apparatus or articles in engineering in general
    • F16C2361/61—Toothed gear systems, e.g. support of pinion shafts
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K5/00—Casings; Enclosures; Supports
    • H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
    • H02K5/16—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields
    • H02K5/173—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields using bearings with rolling contact, e.g. ball bearings
    • H02K5/1735—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields using bearings with rolling contact, e.g. ball bearings radially supporting the rotary shaft at only one end of the rotor

Definitions

  • the present disclosure relates to a system and method for controlling a displacement of a first component relative to a second component, to an engine and to a corresponding controller.
  • Rotating machinery such as gas turbine engines, comprise one or more rotating elements, e.g., shafts.
  • rotating elements e.g., shafts.
  • compressors and/or turbines are mounted to provide for rotation of these components.
  • at least two bearings are provided to allow for a controlled rotation of the shafts.
  • several shafts are provided, which may be coaxial, i.e. with two or more shafts rotating about a common axis. Similar arrangements are also provided in other machine types, in particular other types of aircraft engines.
  • Vibration may be caused by imbalances of the shaft and supported rotatable elements, such as compressor and turbine discs and blades, and also by external forcing such as aircraft maneuvers and aerodynamic forces. Damping systems such as fluid dampers are commonly employed to reduce vibrations.
  • a system comprising a first component being rotatably mounted with respect to a second component, wherein a clearance is provided that allows relative displacement of the first component with respect to the second component other than said rotation.
  • the relative displacement may be a relative translation or a tilting.
  • the system further comprises at least one active device configured to apply a force on the first component, on the second component and/or on a part supporting the first component against the second component, and a controller controlling the active device based on a target value indicative for a range of a displacement (e.g., indicative for a maximum displacement) of the first component with respect to the second component and/or based on a target value indicative for a stiffness of at least one of the first and second components, particularly so as to modify the range of a displacement (e.g., of a maximum displacement) of the first component with respect to the second component.
  • a target value indicative for a range of a displacement e.g., indicative for a maximum displacement
  • a target value indicative for a stiffness of at least one of the first and second components particularly so as to modify the range of a displacement (e.g., of a maximum displacement) of the first component with respect to the second component.
  • the system can be adapted dynamically to different operating conditions, so that the operational characteristics of the system may be significantly improved. In particular, vibrations may be reduced in various operating conditions.
  • the active device is adapted to apply the force on the first component and/or on the second component such that the stiffness (e.g., the static stiffness) of the first component and/or the second component and/or of its mounting is modified. This allows to precisely modify the available displacement for the first component.
  • stiffness e.g., the static stiffness
  • the force that the active device is adapted to apply may be a non-contact force, e.g., a magnetic force or an electric force.
  • a non-contact force e.g., a magnetic force or an electric force.
  • the controller may regulate the non-contact force (in particular by regulating the magnetic flux) to set the target value. It is worth noting that by applying the non-contact force the clearance may be enlarged or decreased.
  • the system may provide an active non-contact stiffness control. In particular, the system can be used for a clearance control.
  • the active device comprises one or more electric coils.
  • the one or more coils may be part of a magnetic bearing or of an electrical drive. This allows a synergistic use of active components.
  • the system may comprise the magnetic bearing.
  • the system may comprise mechanic (e.g., roller or journal) bearings that support the first component.
  • the system may be adapted such that the first component will be operational (and rotatably supported) when the magnetic bearing is deactivated. That is, the mechanical bearings may be adapted to carry the weight and enable operation of the first component, while the controller may be activated, e.g., in certain operational conditions.
  • the active device is adapted to exert a radial force with respect to a rotational axis of the rotation of the first component relative to the second component.
  • the active device is adapted to exert an axial force with respect to a rotational axis of the rotation of the first component relative to the second component.
  • a bearing between the first and second components defines at least a part of the clearance.
  • the bearing may be a roller bearing.
  • Such bearings typically have a clearance. This clearance may vary depending on the operating temperatures and wear. By the active device and the controller described herein this clearance may be actively controlled.
  • the first component is a shaft and the second component is a support structure that carries the shaft.
  • a turbine and/or fan and/or compressor may be mounted on the shaft.
  • the controller stores at least two target values, e.g., displacement-range (e.g., maximum-displacement) and/or stiffness target values (which may be different or the same).
  • each of the at least two (e.g., displacement-range (e.g., maximum-displacement) and/or stiffness) target values may be provided for (and associated with) one of at least two different operating conditions of the system, e.g., a higher-load condition and a lower-load condition.
  • the temperature of the first and/or of the second component is different.
  • one of the operating conditions is a transient condition.
  • blades with variable pitch may be mounted on the shaft.
  • An operation during adjustment of the pitch is an example for such a transient condition.
  • the controller may store a look-up table comprising parameters to control the active device, e.g., for at least two different operating conditions of the system. This allows a simple design of the controller and a precise fine-tuning.
  • the system may further comprise at least one sensor to measure a physical parameter, e.g., a temperature, a displacement of the first component relative to the second component and/or a vibration.
  • the controller comprises a closed loop control.
  • the closed loop may use a value measured by the at least one sensor as feedback parameter. This allows to adapt the control to changing conditions.
  • an engine in particular an engine for an aircraft, is provided.
  • the engine comprises the system according to any aspect or embodiment described herein.
  • the engine may be an electrical engine, a gas turbine engine or a hybrid engine.
  • a controller for controlling the active device of the system of any aspect or embodiment described herein based on a target value for a range of a displacement (e.g., of a maximum displacement) of the first component with respect to the second component and/or based on a target value indicative for a stiffness of at least one of the first and second components.
  • a target value for a range of a displacement e.g., of a maximum displacement
  • a method for controlling a displacement of a first component relative to a second component is provided, the first component being rotatably mounted with respect to a second component, wherein a clearance is provided that allows relative displacement of the first component with respect to the second component, wherein an active device is configured to apply a force on the first component and/or on the second component.
  • the method comprises controlling the active device based on a target value for a range of a displacement (e.g., for a maximum displacement) of the first component with respect to the second component and/or based on a target value indicative for a stiffness of at least one of the first and second components.
  • the method may use the system and/or controller according to any aspect or embodiment described herein.
  • a method to design a component comprises determining an optimal stiffness for a given operating condition by controlling a displacement of a first component relative to a second component in accordance with the method described above for different target values, and determining a design of at least one part of the system based on the determined optimal stiffness.
  • Figure 1 shows an aircraft 8 in the form of a passenger aircraft.
  • the aircraft 8 comprises several (i.e., two) gas turbine engines 10 in accordance with Figure 2 .
  • FIG. 2 illustrates a gas turbine engine 10 having a principal rotational axis 9.
  • the engine 10 comprises an air intake 12 and a propulsive fan 23 that generates two airflows: a core airflow A and a bypass airflow B.
  • the gas turbine engine 10 comprises a core 11 that receives the core airflow A.
  • the engine core 11 comprises, in axial flow series, a low pressure compressor 14, a high-pressure compressor 15, combustion equipment 16, a high-pressure turbine 17, a low pressure turbine 19 and a core exhaust nozzle 20.
  • a nacelle 21 surrounds the gas turbine engine 10 and defines a bypass duct 22 and a bypass exhaust nozzle 18.
  • the bypass airflow B flows through the bypass duct 22.
  • the fan 23 is attached to and driven by the low pressure turbine 19 via a shaft 26 and an epicyclic gearbox 30.
  • the core airflow A is accelerated and compressed by the low pressure compressor 14 and directed into the high pressure compressor 15 where further compression takes place.
  • the compressed air exhausted from the high pressure compressor 15 is directed into the combustion equipment 16 where it is mixed with fuel and the mixture is combusted.
  • the resultant hot combustion products then expand through, and thereby drive, the high pressure and low pressure turbines 17, 19 before being exhausted through the nozzle 20 to provide some propulsive thrust.
  • the high pressure turbine 17 drives the high pressure compressor 15 by a suitable interconnecting shaft 27.
  • the fan 23 generally provides the majority of the propulsive thrust.
  • the epicyclic gearbox 30 is a reduction gearbox.
  • FIG. 3 An exemplary arrangement for a geared fan gas turbine engine 10 is shown in Figure 3 .
  • the low pressure turbine 19 (see Figure 2 ) drives the shaft 26, which is coupled to a sun wheel, or sun gear, 28 of the epicyclic gear arrangement 30.
  • a sun wheel, or sun gear, 28 of the epicyclic gear arrangement 30 Radially outwardly of the sun gear 28 and intermeshing therewith is a plurality of planet gears 32 that are coupled together by a planet carrier 34.
  • the planet carrier 34 constrains the planet gears 32 to precess around the sun gear 28 in synchronicity whilst enabling each planet gear 32 to rotate about its own axis.
  • the planet carrier 34 is coupled via linkages 36 to the fan 23 in order to drive its rotation about the engine axis 9.
  • an annulus or ring gear 38 Radially outwardly of the planet gears 32 and intermeshing therewith is an annulus or ring gear 38 that is coupled, via linkages 40, to a stationary supporting structure 24.
  • the gas turbine engine 10 further comprises an electrical drive 70, see Figure 2 .
  • the electrical drive 70 can be used as a motor and as a generator, but could alternatively be only a motor or generator.
  • the electrical drive 70 comprises a stator that is fixed with respect to the stationary supporting structure 24, and a rotor that is fixed to the one of the shafts 26, 27, here to shaft 26.
  • the gas turbine engine 10 also comprises bearings 60 (one of which is shown in Figure 3 ) and a magnetic bearing 41 for the shaft 26.
  • low pressure turbine and “low pressure compressor” as used herein may be taken to mean the lowest pressure turbine stages and lowest pressure compressor stages (i.e. not including the fan 23) respectively and/or the turbine and compressor stages that are connected together by the interconnecting shaft 26 with the lowest rotational speed in the engine (i.e. not including the gearbox output shaft that drives the fan 23).
  • the "low pressure turbine” and “low pressure compressor” referred to herein may alternatively be known as the "intermediate pressure turbine” and “intermediate pressure compressor”. Where such alternative nomenclature is used, the fan 23 may be referred to as a first, or lowest pressure, compression stage.
  • the epicyclic gearbox 30 is shown by way of example in greater detail in Figure 4 .
  • Each of the sun gear 28, planet gears 32 and ring gear 38 comprise teeth about their periphery to intermesh with the other gears. However, for clarity only exemplary portions of the teeth are illustrated in Figure 4 .
  • Practical applications of a planetary epicyclic gearbox 30 generally comprise at least three planet gears 32.
  • the epicyclic gearbox 30 illustrated by way of example in Figures 3 and 4 is of the planetary type, in that the planet carrier 34 is coupled to an output shaft via linkages 36, with the ring gear 38 fixed.
  • the epicyclic gearbox 30 may be a star arrangement, in which the planet carrier 34 is held fixed, with the ring (or annulus) gear 38 allowed to rotate. In such an arrangement the fan 23 is driven by the ring gear 38.
  • the gearbox 30 may be a differential gearbox in which the ring gear 38 and the planet carrier 34 are both allowed to rotate.
  • any suitable arrangement may be used for locating the gearbox 30 in the engine 10 and/or for connecting the gearbox 30 to the engine 10.
  • the connections (such as the linkages 36, 40 in the Figure 3 example) between the gearbox 30 and other parts of the engine 10 (such as the input shaft 26, the output shaft and the fixed structure 24) may have any desired degree of stiffness or flexibility.
  • any suitable arrangement of the bearings between rotating and stationary parts of the engine may be used, and the disclosure is not limited to the exemplary arrangement of Figure 3 .
  • the gearbox 30 has a star arrangement (described above)
  • the skilled person would readily understand that the arrangement of output and support linkages and bearing locations would typically be different to that shown by way of example in Figure 3 .
  • the present disclosure extends to a gas turbine engine having any arrangement of gearbox styles (for example star or planetary), support structures, input and output shaft arrangement, and bearing locations.
  • gearbox styles for example star or planetary
  • support structures for example star or planetary
  • input and output shaft arrangement for example star or planetary
  • bearing locations for example star or planetary
  • the gearbox may drive additional and/or alternative components (e.g. the intermediate pressure compressor and/or a booster compressor).
  • additional and/or alternative components e.g. the intermediate pressure compressor and/or a booster compressor.
  • gas turbine engines to which the present disclosure may be applied may have alternative configurations.
  • such engines may have an alternative number of compressors and/or turbines and/or an alternative number of interconnecting shafts.
  • the gas turbine engine shown in Figure 2 has a split flow nozzle 20, 22 meaning that the flow through the bypass duct 22 has its own nozzle that is separate to and radially outside the core engine nozzle 20.
  • this is not limiting, and any aspect of the present disclosure may also apply to engines in which the flow through the bypass duct 22 and the flow through the core 11 are mixed, or combined, before (or upstream of) a single nozzle, which may be referred to as a mixed flow nozzle.
  • One or both nozzles may have a fixed or variable area.
  • the described example relates to a turbofan engine, the disclosure may apply, for example, to any type of gas turbine engine, such as an open rotor (in which the fan stage is not surrounded by a nacelle) or turboprop engine, for example.
  • the gas turbine engine 10 may not comprise a gearbox 30.
  • the geometry of the gas turbine engine 10, and components thereof, is defined by a conventional axis system, comprising an axial direction (which is aligned with the rotational axis 9), a radial direction (in the bottom-to-top direction in Figure 2 ), and a circumferential direction (perpendicular to the page in the Figure 2 view).
  • the axial, radial and circumferential directions are mutually perpendicular.
  • the system 1A comprises a first component, a second component, active devices 48A, 48B and a controller 44.
  • the first component is rotatably mounted with respect to the second component, wherein a clearance Ca is provided that allows relative displacement of the first component with respect to the second component.
  • the first component is the shaft 26 that connects the low-pressure turbine 19 with the low-pressure compressor 14, but in general it could be any other shaft of the gas turbine engine 10 or another type of engine.
  • the second component is, in this example, the stationary support structure 24, but it could alternatively be another component, e.g., another shaft, e.g., shaft 27.
  • the stationary support structure 24 will be referred to as structure 24 in the following.
  • the active devices 48A, 48B each are configured to apply a force on parts 64 that support the shaft 26 on the structure 24.
  • the controller 44 is adapted for controlling the active devices 48A, 48B based on a target value indicative for a range of a displacement, specifically for a maximum displacement of the shaft 26 with respect to the structure 24 and/or on a target value indicative for a stiffness of at least one of the shaft and the structure 24 as will be described in more details further below.
  • the controller 44 is a stiffness controller, in particular a non-contact stiffness controller.
  • the shaft 26 is mounted rotatably with respect to the structure 24 by means of a bearing 60, which is a roller bearing comprising a stator 61 that is mounted at the structure 24, a rotor that is mounted on the shaft 26, and a plurality of rolling elements 63.
  • the bearing 60 is a ball bearing in this example.
  • the shaft 26 is rotatable with respect to the structure 24 about the rotational axis 9.
  • the stator 61 of the bearing 60 is secured against the structure 24 by means of several parts 64. These parts may, for example, be or comprise a spacer, a washer, a seal or the like.
  • each of these parts 64 has a stiffness which is denoted as Ka1 to Ka4 in Figure 5 , and illustrated conceptually as springs.
  • the active devices 48A, 48B may be operated.
  • the active devices 48A, 48B comprise a plurality of coils 46 (in this example each coil 46 is wound around a core). Each of the coils 46 is electrically connected to the controller 44.
  • each active device 48A, 48B comprises two coils 46, each one at opposing sides of an anchor 49, but alternatively it is conceivable that each active device comprises only one of such coils 46.
  • the system 1A comprises more than the two active devices 48A, 48B, but a plurality of such active devices distributed around the rotational axis 9. On the other hand, in principle only one active device 48A would also be possible.
  • Each of the active devices 48A, 48B is configured to exert a non-contact force, more specifically, a magnetic force on another part of the system 1A, in the arrangement as shown on the anchor 49.
  • a resulting force Fmag is applied on the anchor 49 (here: in axial direction) and thus on the parts 64 and on the structure 24 and/or on the stator 61 of the bearing 60.
  • the axial clearance Ca becomes smaller or larger and the stiffness of the shaft 26 is reduced or increased.
  • the controller 44 is adapted for controlling the active device 48A, 48B based on a target value indicative for a stiffness of at least one of the shaft and the structure 24. As an alternative or in addition, the controller 44 is adapted for controlling the active device 48A, 48B based on a target value indicative for a maximum displacement of the shaft 26 with respect to the structure 24. Further, the controller 44 stores at least two different target values, each for one of at least two different operating conditions of the system 1A. For example, the two operating conditions may be a high-load condition and a low-load condition. In the high-load condition the components of the system 1A become heated with respect to the low-load condition and, therefore, are expanded.
  • the system 1A is designed such that the bearing 60 allows a low-friction rotation of the shaft 26 in both operating conditions.
  • the clearance Ca is larger than in the high-load condition. Therefore, in the low-load condition the controller 44 may control the active devices 48A, 48B so as to apply a stronger force Fmag compared to the high-load condition.
  • the same stiffness, clearance Ca or maximum displacement or a value indicative therefore is used as target value for the two different operating conditions.
  • different target values are used, e.g., when a larger clearance is necessary in one of the operating conditions with respect to the other.
  • a clearance Ca or maximum displacement (and/or a stiffness) can be the corresponding target value that is larger or smaller than the corresponding target value of a steady condition.
  • the operative condition may be based on the load, e.g., the axial load La that acts on the shaft 26.
  • the target value used by the controller 44 may be based on the load or axial load La.
  • the controller 44 may apply an open loop control based on stored reference values, e.g., stored in a look-up table.
  • the look-up table may comprise an entry for each operating condition.
  • the controller 44 may apply a closed-loop control based on sensor readings as will be described further below.
  • controller 44 sets a static state of a specific target value for the range of displacement, maximum displacement and/or stiffness.
  • this static state is superimposed with a dynamic control to react on vibrations and/or to provide an active damping.
  • the dynamic part is added to the static control target (which serves as a baseline).
  • Figure 6 shows a system 1B similar to system 1A of Figure 5 so that only the differences are explained in the following.
  • the bearing 60 stator 61 is supported via parts 64 against the structure 24 (without interposed anchor).
  • the active devices 48A, 48B act on the rotor 62 of the bearing 60.
  • the active devices 48A, 48B may be designed as described with reference to Figure 5 and are just shown simplified in Figure 6 (and further following Figures).
  • controller 44 (also not shown but present in Figure 6 and following Figures) is as described above.
  • FIG 7 again shows the system 1A of Figure 5 .
  • the different active devices 48A, 48B are not operated such that they apply symmetric forces Fmag, but asymmetrical.
  • the controller 44 of the system 1A is operable to operate the active devices 48A, 48B asymmetrical.
  • an angular clearance ⁇ a can be controlled.
  • a moment such as a bending moment Mb on the shaft 26 leads to different maximum tilting displacement of the shaft 26 or a section thereof with respect to the structure 24, depending on the setting of the controller 44.
  • FIG. 8 A similar angular clearance ⁇ a control is shown in Figure 8 , with the system 1C similar to the system 1B described above with reference to Figure 6 , but where the active devices 48A, 48B act on the shaft 26 (instead of on the bearing 60 rotor 62). Thus a force of the active devices 48A, 48B that indirectly acts on the bearing 60 is transmitted via the shaft 26. (vice versa in the system 1B of Figure 6 ).
  • FIG. 9 Another system 1D is shown in Figure 9 .
  • the active devices 48A, 48B act on parts 64 (which may be one annular part) that are (or is) interposed between a ball bearing 60 stator 61 and the structure 24.
  • the active devices 48A, 48B are configured to exert radial forces Fmag to control a radial clearance Cr defined by the bearing 60.
  • Radial loads Lr lead to a radial displacement of the shaft 26 within the radial clearance Cr.
  • Figure 10 shows another system 1E for radial clearance Cr control similar to system 1D of Figure 9 , but with the active means 48A, 48B acting on the shaft 26, e.g., directly on the shaft 26 or on a part fixedly mounted on the shaft 26.
  • Figure 11 shows the system 1C with additional, optional, sensors 50-53.
  • the sensors 50-53 are arranged on (or in proximity to) the structure, the part 64, the active device 48Bor other locations at which the forces are applied (e.g., bearings 60), and the system 1C (as well as the other systems described herein) may comprise one, more than one or all of these sensors 50-53.
  • the sensors 50-53 may be adapted to measure one or more physical quantities such motion, offsets, angular positions, vibration, torque, force, moment, temperatures, and engine parameters and the like.
  • the sensors 50-53 are communicatively connected to the controller 44.
  • the controller 44 may receive signals from a FADEC such power, NGV positions, fuel intakes or the like in order to define the state of the performance regulation of the engine.
  • signals from a FADEC such power, NGV positions, fuel intakes or the like in order to define the state of the performance regulation of the engine.
  • One or more of these signals can be used for controlling magnitude, directions and time of application of the non-contact forces (to apply non-contact stiffness) and, optionally, to close a control loop of the controller 44, in order to allow an enlarged or restricted clearance gap.
  • a look-up table can be used to activate, deactivate and/or change direction and/or magnitude of the non-contact forces (to apply non-contact stiffness) to achieve the clearance control.
  • the look-up table may contain values obtained by FE calculations and/or test results.
  • a peripheral interface controller, PIC can send a batch of signals to engine (e.g., of gas turbine engine 10) controllers, for conjoint regulations.
  • Dynamic functions such as active damper can be introduced using the non-contact forces or other systems (e.g., speed controllers) in order to stabilize the system response in transient conditions.
  • Figure 12 shows a diagram with the static displacement, e.g., of the bearing 60 stator 61 or rotor 62.
  • the interval 0-C denotes the mechanical clearance, i.e., the range in which the bearing 60 can move.
  • the bearing 60 parts make contact.
  • Further displacement by increasing load L, e.g., point L0, 50, is based on the stiffness of the mounting, e.g. parts 64, until point D.
  • a range may be restricted, as indicated with ⁇ 0 ⁇ .
  • Curves a1, a2, ... an indicate possible control curves of the controller 44.
  • the control curves define load-dependent target value indicative for a maximum displacement of the shaft 26 relative to the structure 24.
  • the load L is, e.g., a radial or axial load or a moment on the shaft 26. (e.g., with respect to the structure 24).
  • the corresponding stiffness is the tangent of the respective curve.
  • the non-contact magnetic stiffness is used as the target value, e.g., determined from a look-up table that stores target values for different operating conditions. All these variables may be, e.g., dependent on time, Temperature and/or speed.
  • Figure 13 shows the system 1D described above, with additional sensors 54, 55 that measure the distance between the structure 24 and the shaft 26 or the bearing 60 stator 61, respectively.
  • a functional drawing is added indicating the different stiffness of the various parts and, particularly, the variable stiffness KmagA and KmagB added by the non-contact forces.
  • the radial clearance Cr (that may be dependent on variables such as time, speed and/or temperature) may thus be calculated as dividing the resultant load (taking into account feedback) divided by the sum of mechanical and magnetic stiffness.
  • the right part of the Figure shows clearance and maximum displacement target values for different operating conditions at different points in time.
  • Figure 14 shows a system 1F with a magnetic bearing 41 that may additionally or alternatively be used as active device in any of the systems described herein.
  • a plurality of salient teeth 45 project inwardly from the structure 24.
  • Coils 46 are wound round each salient tooth 45, and are coupled to an electrical power supply of the controller 44 or controlled by the controller 44.
  • An optional rotor lamination 47 mounted around the shaft 26 rotates with the shaft 26, and comprises a magnetic material such as iron. Activation of some or all of the coils 46 allows an asymmetric or symmetric increase of the shaft 26 stiffness.
  • the controller 44 may control the magnetic bearing 41 based on a target value (e.g., indicative for a maximum displacement of the shaft 26 with respect to the structure 24 and/or for a stiffness).
  • Optional sensors 43, 44 e.g., distance sensors, may be used as input to the controller 44 for a closed loop control.
  • the magnetic bearing 41 does not carry the shaft 26.
  • the magnetic bearing may be switched off and the shaft will be carried by its mechanical bearings. The same holds for the active devices 48A, 48B.
  • the electrical drive 70 of the gas turbine engine 10 may additionally or alternatively be used as an active device by the controller 44 of any system described herein. Further, an air-compressed bearing may be used.
  • Figure 15 shows a method for controlling a displacement of a first component (e.g., the shaft 26) relative to a second component (e.g., the structure 24), the first component being rotatably mounted with respect to the second component, wherein a clearance Ca, Cr, ⁇ a is provided that allows relative displacement of the first component with respect to the second component, wherein an active device is configured to apply a force on the first component, on the second component and/or on a part supporting the first component against the second component.
  • a clearance Ca, Cr, ⁇ a is provided that allows relative displacement of the first component with respect to the second component
  • an active device is configured to apply a force on the first component, on the second component and/or on a part supporting the first component against the second component.
  • the method comprises step S10: controlling the active device based on a target value indicative for a range of a displacement, e.g., for a maximum displacement, of the first component with respect to the second component and/or on a target value indicative for a stiffness of at least one of the first and second components 26, 24.
  • Figure 15 further shows a method to design a component, comprising: step S1: determining an optimal stiffness for a given operating condition by controlling a displacement of a first component relative to a second component in accordance with step S10 for different target values; and step S2: determining a design of at least one part of the system based on the determined optimal stiffness.
  • adjustable non-contact stiffness can be utilized in rigs (e.g. power gearbox, PGB, tests) in order to characterize which are the optimal stiffness and clearances trade-offs for the final design.
  • Output of the test would be the definition of the mechanical clearances, and stiffness of the static deformable structures, to be used in the next design iteration.
  • controller 44 may close a control loop on one or more of displacement sensor(s), current(s) of magnetic-flow signals and the effect of non-contact stiffness using look-up tables.
  • the controller 44 optionally includes a damping, e.g., proportional to the frequency or velocity of a vibration, as measured by one or more vibration sensors.
  • a damping may be added with a 90 degrees phase lag with respect to the displacement of the first component with respect to the second component.
  • the damper effect can act like a structural damping with a complex stiffness where the real part is the non-contact stiffness and the imaginary part is the damping.
  • the discussed magnetic loads may be applied in difference locations in order to control clearances between different rotors and rotors and statoric parts to defined targets.
  • the desired level of stability of the system can be obtained by tuning the response of the system (and, optionally, by having in place a design concept where the rotors are isostatic or hyper-static on contact bearing (rolling journal etc.).
  • the non-contact forces may be applied on rotors and/or stators, so that the motion allowed to the rotors or to elastic or movable static parts, that can take place within the available clearances, can be limited as required in one or more predefined operating conditions (e.g., throughout the engine operational envelope).
  • the system stiffness can be controlled and variated in a different manner at each speed and load condition, in order to optimize the position of the rotors at any operational condition.
  • the clearances between rotors or between rotors and stators in an aircraft engine may be determined in order to accommodate the largest displacements that are necessary for assembly, to compensate thermal growth and to undergo the operational loads without generating over-stress peaks.
  • the non-contact forces can be provided by the application of electromagnetic forces, e.g. developed in electrical drives or magnetic bearings in order to control clearances between different rotors and rotors and stator parts.
  • auxiliary systems and/or active control methods may also apply auxiliary systems and/or active control methods to reduce a magnetic contamination that the stiffness controller 44 may induce on other (e.g., magnetic sensitive) devices on the engine (e.g., interferences on chip detectors of a PGB may be mitigated when the non-contact stiffness control is actuated to optimize the stiffness of a ring gear mounting of a planetary gearbox).
  • active e.g., generating an opposing magnetic field
  • passive e.g. by arranging a shield, e.g., mu-metal shield, between the active device and the other device

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Power Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Microelectronics & Electronic Packaging (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Magnetic Bearings And Hydrostatic Bearings (AREA)
EP20205717.0A 2020-11-04 2020-11-04 System und verfahren zur steifigkeitssteuerung Pending EP3995671A1 (de)

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5347190A (en) * 1988-09-09 1994-09-13 University Of Virginia Patent Foundation Magnetic bearing systems
US20190360357A1 (en) * 2018-05-25 2019-11-28 General Electric Company System and Method for Mitigating Undesired Vibrations at a Turbo Machine
EP3670942A1 (de) * 2018-12-17 2020-06-24 Rolls-Royce plc Lageranordnung mit aktiver schwingungsregelung

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5347190A (en) * 1988-09-09 1994-09-13 University Of Virginia Patent Foundation Magnetic bearing systems
US20190360357A1 (en) * 2018-05-25 2019-11-28 General Electric Company System and Method for Mitigating Undesired Vibrations at a Turbo Machine
EP3670942A1 (de) * 2018-12-17 2020-06-24 Rolls-Royce plc Lageranordnung mit aktiver schwingungsregelung

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